Detonation combustion of a gas mixture in a cylindrical chamber

Continuous spin detonation of fuel-air mixtures

“…The ratio of the TDW size to the distance between the waves is h/l = 1/4-1/3 (l = πd ch for n = 1). For FOMs, the ratio is h/l = 1/10-1/5 [9]. The difference in the dimensionless width of the detonation front for FAMs is caused by the following reasons: absence (or insufficient development) of the combustion front on the side of combustion products and supersonic velocity of the mixture in the laboratory coordinate system ahead of the TDW front.…”

Mathematical modeling of a rotating detonation wave in a hydrogen-oxygen mixture

“…The flow velocity at the exit of a constantsection combustor is supersonic, while it is known to be sonic in the one-dimensional process of conventional combustion. The one-dimensional model of continuous rotating (spin) detonation in a cylindrical combustor [5,10] can predict the basic parameters of the flow with TDWs in an annular combustor if experimental values of the relative size of the TDW and the angle of inclination of the wave to the combustor axis are available. The mathematical model of spin detonation in a two-dimensional steady formulation [10][11][12] with the transition to the TDW-fitted coordinate system made it possible to calculate (avoiding the use of experimental information) a detailed two-dimensional periodic flow field and relative sizes of the TDW and shock-wave tail and to demonstrate that there is a transonic transition in a constant-section combustor in the spin detonation regime.…”

“…The regime of detonation combustion of the fuel mixture continuously injected into an annular chamber with exit constriction [9] or without the latter [5] was theoretically examined in a one-dimensional approximation under the assumption of a uniform flow of detonation products with a sonic velocity in the axial direction. In this case, the output parameters of the flow were uniquely determined by the combustor geometry and thermochemical and gas-dynamic constants of the fuel mixture and were independent of the combustion mechanism.…”

“…This method allows intense and more thermodynamically efficient and stable combustion of various fuels in combustors of moderate size determined by the characteristic size of the detonationwave front [1][2][3][4][5][6][7][8].…”

Numerical study on three-dimensional flow field of continuously rotating detonation in a toroidal chamber

“…Such rotating detonations have been experimentally observed by Voitsekhovskii [2] as early as 1959, and then Mikhailov [3] analyzed the structure of the detonation wave. In 1980s, Bykovskii's [4] experiments verified the possibility of controlling rotating detonation wave by using gaseous and liquid propellant fuel and injecting the fuel at subsonic speed in varying cross-section and constant sections of an annular combustor. In recent years, investigations on the detonation engine have become popular, related researches have been done in France, America, Russia, Japan etc., and meaningful results have been obtained [5][6][7][8][9][10].…”